Integrated flow turbine engine

An integrated flow turbine engine comprising a housing, a rotor mounted for high speed rotation in said housing, said rotor having a single set of identical blades affixed to it, said rotor with said blades serving both as a compressor and as a turbine, at least one combustion chamber disposed in said housing at a location in close proximity to said rotor, a plurality of substantially arcuately shaped wall components defining a boundary between said rotor and said combustion chamber, said wall components being spaced somewhat apart to accommodate the flow of gases between said combustion chamber and said rotor, said combustion chamber having means therein for the injection of fuel such that a controlled amount of combustion can be brought about in said combustion chamber, said blades of said rotor being one piece, elongate members, having substantially cuneiform edge portions, said combustion chamber having at least one inlet means through which air compressed as a result of the rotation of said blades can be caused to enter, said inlet means being adjacent said cuneiform edge portions of said blades, said combustion chamber also having a plurality of exit nozzles, said exit nozzles being on the same side of said rotor as said inlet means, at circularly different locations, and having flow axes at an acute angle to the path of said cuneiform edge portions of said blades, through which exit nozzles, combustion products generated in said combustion can react against said cuneiform edge portions and thus bring about the driving of said rotor at high speeds.

An integrated flow turbine engine comprising a housing, a rotor mounted for high speed rotation in said housing, said rotor having a single set of identical blades affixed to it, said rotor with said blades serving both as a compressor and as a turbine, at least one combustion chamber disposed in said housing at a location in close proximity to said rotor, a plurality of substantially arcuately shaped wall components defining a boundary between said rotor and said combustion chamber said wall components being spaced somewhat apart to accommodate the flow of gases between said combustion chamber and said rotor said combustion chamber having means therein for the injection of fuel such that a controlled amount of combustion can be brought about in said combustion chamber, the blades of said rotor being one piece, elongate members, said combustion chamber having at least one inlet means through which air compressed as a result of the rotation of said blades can be caused to enter, said combustion chamber also having at least one exit nozzle, said exit nozzle being on the same side of said rotor as said inlet means, but at a circularly different location, through which exit nozzle, combustion products generated in said combustion chamber can exit, said blades each having an edge portion arranged to pass near said exit nozzle during rotation of said rotor, so that combustion products emanating from said combustion chamber can react against said edge portions and thus bring about the driving of said rotor at high speeds, a centripetal flow arrangement thus being defined, with the combustion products from said exit nozzle of said combustion chamber flowing radially outwardly so as to impinge upon said edge portions of said blades, with the combustion products thereafter turning and then flowing substantially radially inwardly, and exhaust collection means disposed radially inwardly of said rotor, into which the combustion products then flow.